Aeroplane



C. H. CASPAR.

AEROPLANE.

APPLICATION FILED ocr. 15. 1918,

Patented Nov. 30,1920.

5 SHEETSSHEET I.

c. H. CASPAR.

AEROPLANE.-

APPLICATION FILED on. 15. [918.

y L J Patented Nov. 30, 1920.

C. H, CASPAR.

AEROPLANE.

APPLICATION FILED 0cT.15. 1918.

1,360,621. Patented Nov. 30, 1920;

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' UNITED STATES PATENT--OFFICE.

CHARLES H. cnsmmfor rnrLADELrH'Ia, PENNSYLVANIA.

AEBOPLANE.

To all whom it may concern:

Be it known that I, CHARLES H. CAsrAR, a citizen of the United States, residing in Philadelphia", Pennsylvania, have invented certain Improvements in Aeroplanes, of which the following is a specification.

My invention relates to aeroplanes; and one object of my invention is to provide a structure of greater size, greater lifting power, and greater carrying capacity than other structures having a similar object in view, or designed for a similar purpose.

A further object of my invention is to provide a structure particularly available for military purposes and capable of sustaining in flight a relatively large crew beside an operator (or operators) and, in addition, a structure that may be equipped with a main battery of guns having arelatively larger caliber and more efiective range than those employed with aeroplanes heretofore con structed or developed.

A further object of my invention is to provide novel means for applying power to drive aeroplane structures; the same being particularly adapted for a structure of the type forming the subject of my invention.

A further object of my-invention is to provide a structure having hollow wing vanes with flexible tips; the chambers of such vanes communicating with a power duct (or ducts) throughwhich astream (or streams) of air will be forced by the propelling means employed.

And a further object of my invention is to provide a boat-like structure, which while it may carry suitable wheel supports or other means whereby it may run upon the ground preliminary to or after flight, may have a suitable floating body. in lieu of such wheel supports, structure being designed to rise from the water as well as from the ground.

These and other features of my invention are more fully described hereinafter, reference being had to the accompanying drawings, in which:

igure 1, is a plan view of an aeroplane structure within thescope of my invention. Fig. 2, is a front elevation ofthe same. Fig. 3, is a side elevation. 4

Fig. 4, is a longitudinal section on the line IV--IV, Fig. 5.

Fi 5, is a sectional plan view onthe line V- Fig. 4.

as may be desired; my'improved- Specification of Letters Patent; Patented Ngv, 30 1920, Application filed October 15, 1918. Serial No. 258,282.

Figs. 6, 7 and 8, are cross'sectional views on the lines VIVI, VII-VII, and VIII- VIII, Fig. 4.

Fig. 9, is an enlarged plan view of one of the wings.

Fig. 10, is a sectional view of the wing, on

the line XX, Fig. 9, and

Fig. 11, is a cross sectional view of a wing on the line XI--XI, Fig. 9, at its point 0 attachment with the body.

The body of my improved aeroplane structure, illustrated at 1 in the several v term a power duct. If more than one propeller is employed, there may be a power duct for each propeller. Connected to the body 1, externally of the same at several points throughout its length are a series of ollow wings 5, having pivotally mounted tips 6, the present structure showing four pairs of such wings connected to the sides of the body at substantially the horizontal axis of the same, while two other pairs may be secured to the sides of the body at points I intermediate the three forward pairs of wings and near the upper portion. of such body. It will be understood that I may employ a greater or less number of such wings, depending upon the size of the structure, and that the1r position with respect to the body is not arbitrary. The body may be provided with port holes or windows 7 closed by the usual form of dead lights common to ship construction.

Within the lower portion of the hollow body below the floor 8 of the power duct; which portion may be water-tight so as to be capable of floating in water, I provide a series of compartments 10, 11, 12, 13 and 14, as follows: The navigators room, indicated at 10, is at the forward part of the structure and may be provided with suitable controlling members 15, having suitable connections 16, whereby the pivoted tips 6 of the wings may be operated as well as the rudder 17-. The latter may becarried by a shaft 18 suitably mounted at the tail of the structure. Behind the navigators room bottom of the structure, and aft of the gun room may be located the engine room 12, preferably centrally of the structure. With fuel tanks 20 flanking the same, and suitable oil receptacles 21 disposed below the engine platform 22 and within the shell of the aeroplane structure. Aft of the engine is the compartment 13 constituting the crews quarters, and aft of the same the compartment 14 provides a mess room. Below thecrews quarters storage space, indicated at 23, may be provided for bombs and other munitions, and in such space a bomb firing pit 24 may be located at any suitable point; here shown as substantially midway the length of the aeroplane structure. It will be understood that any part of the structure may be modified to suit convenience or necessity when the structure is in use.

If designed to rise from and descend to the surface of a body of water, so-called landing gears are not required, but for the purpose of moving the structure over the ground when not in flight, or when commencing flight from the ground and landing, suitable brackets 25, carrying wheels 26 may be attached to the body of the structure.

As a military structure, the upper por-,

tion of the body may be provided with an armored' gun room 30; suitably mounted guns being indicated at 31. An inclosed shaft 33 provides access from the crews quarters to the armored gun room, and within the said shaft a suitable ladder or staircase 34: may be provided, with a suitable ammunition hoist 35 conveniently arranged or paralleling the ladder.

The wings may be of the peculiar shape and character clearly indicated in Figs. 9, 10 and 11, and they may constitute a hollow frame 5, which may be of the usual stream line contour, and the inner ends of such wing frames maybe rigidly attached at 40 to the body 1 of the aeroplane structure; the openings leading to the hollow spaces of the same registering with openings 41 in the wall of the hollow space of the aeroplane structure which I have termed the power duct. The wall of the hollow space in each wing is provided with an opening 42 through which air entering such hollow wlng may escape, and while this opening may be disposed at any convenient point, I

1 have shown it at the rear of such hollow space and under the wing.

Each wing Wlll be preferably provided at its extremity with a movable tip 6, connected to the wing by a hinge joint, the rod 43 of which joint constitutes a shaft; a suitable bearing 44 for its inner end being mounted on the body of theaeroplane, and

this end of the shaft is preferably provided with an operating wheel 45 over which the connecting tiller ropes 16 will pass and thence to the controls of the navigators room, so that such pivoted tips nay be operated as desired. It will be understood that the tips of the oppositely placed wings may be connected to operate together to neutralize the pressure action, and that if desired each wing-tip-may be independently operated.

A propeller 50, diagrammatically illustrated, may be mounted at the forward end of the power duct, and the same may be provided with any desired number of blades. It will be understood, of course, that more than one propeller may be employed, and

.that the disposal of the propelling means The body of the car may be substantially circular in cross section, tapering to a size materially smaller than the main portlon of the same, and pivotally connected to the end is the rudder 17, of suitable construction, mounted on the shaft 18, journaled in suitable bearings 51 carried by the tail of the frame; said shaft having a wheel 52 with a tiller rope 16 passing to one of the controls in the navigators room, whereby such rudder may be shifted laterally in either direction as may be necessary or desirable the operation of the structure.

The operation of my'im'proveYl structure is substantially as follows The propelling means being in action, the motion will create what is commonly. known as thrust, which will tend to pull the structure forward and at the same time force the air reajrwardly throughout the power duct (or ducts) at a velocity which may be as great as 206,) miles perhour. Under such conditions the, structure would, as in the case of an ordinary aeroplane, start to move forward by means of the thrust of the propelling means, and the air passing through the slots in the hollow wings would create an upward thrust on the Wings. If the hinged ends of wings" were turned down so that this." rearwardly discharging air im' pinges-on the same, the tendency of the pressure is to neutralize the forward thrust and force the structure rearward. At a. sufficient velocity the pressure under the wings will raise the structure which, after it hasattained a certain height, if the movement' of the propelling meansor the velocity of the air passing through the power duct is lowered, the machine will descend. While the structure isin vertical flight, the sustaining power and the thrust power are neutralized by turning down the movable By proper adjustment of the movable wing tips and rudder while in a sustained position, the structure may turn on its own axis, or nearly so. Preferably two or more of the rear Wing tipsare connected to a separate control and may be used to control or balance the structure, or for flight up or down, at an angle.

-It follows that, without departing from the spirit of my invention, any source of power may be used pose; for instance, used to create thedesired' blast of air in the power duct, or compressed air may be used. Further, the propelling means may be placed at any desired. position in the structure, as it is not necessary to place it at the forward end. Any desired number of pro-- pelle'rs maybe employed as may be necessary for the size of the structure.

to accomplish the pursteam pressure may be Iclaim:

1. An aeroplane structure comprising a hollow body having a power duct in the upper portion of the same, hollow wings communicating with "said power duct, propelling means mounted in the power duct,

and chambers constitutin crews uarters.

fuel and munition spaces below said power duct.

2. An aeroplane structure comprising" a hollow body having a power duct in the upper portion of the same, hollow wings with outlets communicating with said power duct, a propeller within said power duct, and chambers constituting crews quarters, guel and munition spaces below said power uct.

3. In an aeroplane structure, a hollow body, a power duct in said body, hollow wings communicating with said power duct, a space for engine, fuel, munitions and crews? quarters below said power duct, a gun chamber at the upper portion of the structure, and a shaft between the crews quarters .and said gun chamber passing through the power duct.

CHARLES H. CASPAR. 

